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US 9,284,853 B2Granted
System and method for integrating sections of a turbine
AssigneeGeneral Electric Company
InventorsDeepesh Dinesh Nanda, Gunnar Leif Siden, Craig Allen Bielek
Life of this patent
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Abstract
A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.
Claims10
A system, comprising:
- a gas turbine, comprising:
- a last stage bucket section having a first annular outer wall that is angled with respect to a centerline of the gas turbine at a first angle average;
- and
- an axial diffuser section disposed immediately downstream of the last stage bucket section, the axial diffuser section having a second annular outer wall that is angled with respect to the centerline of the gas turbine at a second angle average for improving radial swirl,
- wherein the first angle average is approximately 20-30 degrees, the second angle average is approximately 12-20 degrees, the first angle average is approximately 2-15 degrees greater than the second angle average, the last stage bucket section and the axial diffuser section couple to one another at a transition point, and a first angle of the last stage bucket section with respect to the centerline is greater than a second angle of the axial diffuser section with respect to the centerline at the transition point.
2 more elements
A system, comprising:
- a gas turbine having an outer wall transition from a last stage bucket outer wall directly to an axial diffuser section outer wall, wherein the last stage bucket outer wall is angled away from a centerline of the gas turbine at a first angle that is approximately 2-15 degrees greater than a second angle at which the axial diffuser section outer wall is angled away from the centerline of the gas turbine at the outer wall transition, wherein the first angle is approximately 20-30 degrees, and the second angle is approximately 12-20 degrees.
A method, comprising:
- providing a last stage bucket section of a gas turbine that is outwardly angled with respect to an axial centerline of the last stage bucket section from a first axial end of the last stage bucket section to a second axial end of the last stage bucket section at a substantially constant first angle;
- providing an axial diffuser section of the gas turbine that is outwardly angled with respect to an axial centerline of the axial diffuser section at a first axial end of the axial diffuser section at a second angle;
- providing the last stage bucket section that is outwardly angled at the substantially constant first angle of approximately 20-30 degrees, and the axial diffuser section that is outwardly angled at the second angle of approximately 12-20 degrees;
- and
- attaching the second axial end of the last stage bucket section to the first axial end of the axial diffuser section at a transition point, wherein the first angle is approximately 2-15 degrees greater than the second angle at the transition point.
2 more elements
Dependencies are inferred from the claim text.